EP0921071A2 - Schalldämpfer für Strahltriebwerk - Google Patents

Schalldämpfer für Strahltriebwerk Download PDF

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Publication number
EP0921071A2
EP0921071A2 EP98307284A EP98307284A EP0921071A2 EP 0921071 A2 EP0921071 A2 EP 0921071A2 EP 98307284 A EP98307284 A EP 98307284A EP 98307284 A EP98307284 A EP 98307284A EP 0921071 A2 EP0921071 A2 EP 0921071A2
Authority
EP
European Patent Office
Prior art keywords
honeycomb core
cell walls
cells
outer layer
acoustic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP98307284A
Other languages
English (en)
French (fr)
Other versions
EP0921071A3 (de
Inventor
Fredrick Hutto
Charles A. Parente
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Vought Aircraft Industries Inc
Original Assignee
Northrop Grumman Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Northrop Grumman Corp filed Critical Northrop Grumman Corp
Publication of EP0921071A2 publication Critical patent/EP0921071A2/de
Publication of EP0921071A3 publication Critical patent/EP0921071A3/de
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B64D33/06—Silencing exhaust or propulsion jets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/14—Boundary layer controls achieving noise reductions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0226—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0253—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
    • B64D2033/026—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates generally to jet engine noise suppression and more particularly to an extended reaction acoustic liner for mitigating jet engine noise by enhancing viscous acoustic losses within the liner, so as to facilitate enhanced acoustic energy dissipation.
  • the jet engine inlet and exhaust duct walls are constructed with noise absorbing material. This is particularly desirable for commercial passenger aircraft, since such aircraft are required to meet stringent government noise regulations. Such noise suppression for commercial passenger aircraft is also desirable so as to enhance the comfort of the passengers thereof.
  • DYNAROHR a registered trademark of Rohr Industries, Inc.
  • the DYNAROHR product is formed of a honeycomb material which is disclosed in United States Patent No. 4,379,191, the contents of which are hereby incorporated by reference.
  • This honeycomb material comprises a core having a plurality of open cells. The core is sandwiched between an outer non-porous layer and an inner porous layer. The inner porous layer is in fluid communication with the open cells of the honeycomb material.
  • a microporous sheet material such as one comprised of finely woven stainless steel cloth, is bonded over the porous sheet and forms a part of the inner surface of the jet engine's inlet duct.
  • the present invention specifically addresses and alleviates the above mentioned deficiencies associated with the prior art. More particularly, the present invention comprises an extended reaction acoustic liner for use in jet engine noise mitigation.
  • the liner comprises a substantially non-porous outer layer, a honeycomb core disposed in laminar juxtaposition to the outer layer, and a porous inner layer in laminar juxtaposition to the honeycomb core, such that the honeycomb core is sandwiched between the outer layer and the inner layer.
  • the honeycomb core comprises a plurality of cell walls defining a plurality of cells. At least some of the cells are in fluid communication with one another via openings formed in the cell walls.
  • the number of cells which are in fluid communication with one another is determined by the degree of viscous acoustic loss desired.
  • a cell may be in fluid communication with one or more of its neighbors.
  • a cell may be in fluid communication with some or all of its neighbors.
  • the number of neighbors with which a cell is in fluid communication may vary from one cell to another.
  • one cell may be in fluid communication with two of its neighbors while another cell is in fluid communication with three of its neighbors.
  • the openings in the cell walls cause viscous acoustic losses, thereby resulting in acoustic energy dissipation according to well known principles.
  • acoustic energy dissipation desirably enhances noise attenuation, thereby substantially reducing the intensity of noise radiated by a jet engine or the like.
  • substantially all of the cells are in fluid communication with one another.
  • substantially all of the cells have openings formed therein such that a fluid communication path is generally defined from any cell, to any other cell.
  • the size and number of openings in the cell walls are configured to provide the desired acoustic resistance.
  • the honeycomb may be comprised of metal, composite, or any other desired material.
  • the porous inner layer preferably comprises either a linear inner layer or a non-linear inner layer.
  • a linear inner layer is defined by a micro-porous material, while a non-linear inner layer is defined by a perforate inner layer.
  • a plurality of alternating layers of honeycomb core and porous inner layer are disposed in laminar juxtaposition to the outer layer such that each layer of honeycomb core comprises a plurality of cells, some of the cells within at least one of the layers of honeycomb being in fluid communication with one another via openings formed in the cells walls thereof.
  • the extended reaction acoustic liner of the present invention may comprise multiple layers of honeycomb material, alternate ones of which comprise cells which are in fluid communication with one another, while the layers of honeycomb between these comprise cells which are not in fluid communication with one another.
  • the first and third layers may comprise walls having openings formed therein, while the second and fourth layers lack such openings.
  • the layers of honeycomb are separated by porous inner layers.
  • each layer of honeycomb core in a multilayer acoustic liner comprises cells which are in fluid communication with one another.
  • any desired combination of honeycomb core layers and/or porous inner layers may be utilized, wherein any of the honeycomb core layers may comprise a plurality of cells which are in fluid communication with one another or no cells which are in fluid communication with one another.
  • the extended reaction acoustic liner of the present invention is illustrated in Figures 1 and 2, which depict two presently preferred embodiments thereof.
  • the first embodiment of the extended reaction acoustic liner 10 comprises a substantially non-porous outer layer 12, a porous inner layer 14, and a honeycomb core 16a disposed intermediate the outer core 12 and the inner core 14.
  • the outer layer 12, the inner layer 14, and the honeycomb core 16a may be comprised of any desired material.
  • the outer layer 12, the inner layer 14, and the honeycomb core 16a may be comprised of composite materials, plastics, and/or metal, in any desired combination thereof.
  • a plurality of openings 18 are formed in the cell walls 20 so as to place adjacent cells 22 in fluid communication with one another.
  • openings 18 are determined according to well known principles so as to provide the desired viscous acoustic losses. Thus, according to the present invention, some or all of the cells 22 are interconnected via openings 18. As those skilled in the art will appreciate, openings 18 may be formed in any wall 20 of any cell 22, as desired.
  • the aspect ratio of the honeycomb core is defined by the width (W) of a cell divided by the length (L) thereof and may be varied, as desired.
  • the honeycomb core 16a shown in Figure 1 has an aspect ratio of approximately one, i.e., the width (W) of each cell 22 is approximately equal to the length (L) thereof.
  • each cell of the honeycomb core 16b is approximately twice the length thereof, thus giving an aspect ratio of approximately two.
  • the aspect ratio of the cells 22 of the honeycomb core may be varied, as desired, so as to provide the required structural and acoustic properties.
  • the dimensions of the extended reaction acoustic liner of the present invention may be varied, as desired.
  • the outer layer 12 and the inner layer 14 may have a thickness of 1/32 inch to 1/8 inch, as desired, and the honeycomb core 16a, 16b, may have a thickness of 1/16 inch to 1 inch, as desired.
  • various different cell sizes are contemplated.
  • the honeycomb core 16a, 16b may comprise cells having diameters or wall to wall dimensions of 1/8 inch, 3/8 inch, 1/2 inch, or 3/4 inch, or any other dimension, as desired. It is further contemplated that a non-uniform cell size may be desirable, wherein the diameters or wall to wall dimensions of the cells may vary, from one cell to another within a given honeycomb core 16a, 16b and/or from layer to layer.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
  • Exhaust Silencers (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
EP98307284A 1997-12-02 1998-09-09 Schalldämpfer für Strahltriebwerk Withdrawn EP0921071A3 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US982710 1997-12-02
US08/982,710 US5923003A (en) 1996-09-09 1997-12-02 Extended reaction acoustic liner for jet engines and the like

Publications (2)

Publication Number Publication Date
EP0921071A2 true EP0921071A2 (de) 1999-06-09
EP0921071A3 EP0921071A3 (de) 2000-06-28

Family

ID=25529438

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98307284A Withdrawn EP0921071A3 (de) 1997-12-02 1998-09-09 Schalldämpfer für Strahltriebwerk

Country Status (2)

Country Link
US (2) US5923003A (de)
EP (1) EP0921071A3 (de)

Cited By (1)

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CN108725807A (zh) * 2017-04-25 2018-11-02 空中客车运营简化股份公司 声学处理面板及飞行器

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